Apparatus and methods for controlling a spacecraft for a transfer orbit. The spacecraft includes a momentum subsystem that stores angular momentum relative to a center of mass of the spacecraft, and a propulsion subsystem that includes electric thrusters. A controller identifies a target spin axis for the spacecraft, determines gimbal angles for electric thruster(s) that so that thrust forces from the electric thrusters are parallel to the target spin axis, and initiates a burn of the electric thruster(s) at the gimbal angles. The controller controls the momentum subsystem to compensate for a thruster torque produced by the burn of the electric thrusters. The momentum subsystem is able to produce a target angular momentum about the center of mass, where a coupling between the target angular momentum and an angular velocity of the spacecraft creates an offset torque to counteract the thruster torque.


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    Titel :

    Spin stabilization of a spacecraft for an orbit maneuver


    Beteiligte:
    WANG QINGHONG W (Autor:in) / SOBEL ALEXANDER JACOB (Autor:in) / LEMKE GARY (Autor:in) / LUI TIMOTHY (Autor:in) / LEE KANGSIK (Autor:in) / CAPLIN GLENN N (Autor:in) / FONTANA TROY ALLEN (Autor:in)

    Erscheinungsdatum :

    2018-05-08


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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